Delta-v budget (or velocity change budget) is a term used in astrodynamics and aerospace industry for velocity change (or delta-v) requirements for the various propulsive tasks and orbital maneuvers over phases of the space mission. Orbital mechanics or astrodynamics is the application of Celestial mechanics to the practical problems concerning the motion of Rockets and other Spacecraft This article is about the field of research and industry for the corporation see The Aerospace Corporation Aerospace comprises the In Astrodynamics, the term delta-v, literally "change in velocity" (see symbol delta) has a specific meaning it is a Scalar which takes Spacecraft propulsion is any method used to change the velocity of Spacecraft and artificial Satellites There are many different methods In Spaceflight, an orbital maneuver is the use of propulsion systems to change the Orbit of a Spacecraft. Spaceflight is the use of Space technology to fly a Spacecraft into and through Outer space.
Sample delta-v budget will enumerate various classes of manoeuvres, delta-v per manoeuvre, number of manoeuvres required over the time of the mission.
In the absence of an atmosphere and landings where the ground is hit with some speed, the delta-v is the same for changes in orbit the other way around: gaining and losing speed cost an equal effort. Landing is the last part of a Flight, where a flying Animal, Aircraft, or Spacecraft returns to the ground
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Launch/landing budget
- Launch to LEO — this not only requires an increase of velocity from 0 to 7. A Low Earth Orbit (LEO is generally defined as an Orbit within the locus extending from the Earth’s surface up to an altitude of 2000 km 8 km/s, but also typically 1. 5–2 km/s for atmospheric drag and gravity drag
- Re-entry from LEO — the delta-v required is the orbital manoeuvring burn to lower perigee into the atmosphere, atmospheric drag takes care of the rest. In Fluid dynamics, drag (sometimes called fluid resistance) is the force that resists the movement of a Solid object through a Fluid (a In Astrodynamics and Rocketry, gravity drag (or gravity losses) is the difference between the Delta-v expended and the actual change in speed
Stationkeeping budget
| Maneuver | Average delta-v per year [m/s] | Maximum per year [m/s] | |||
|---|---|---|---|---|---|
| Drag compensation in 400–500 km LEO | <25 | <100 | |||
| Drag compensation in 500–600 km LEO | < 5 | < 25 | |||
| Drag compensation in > 600 km LEO | < 7. 5 | ||||
| Station-keeping in geostationary orbit | 50 – 55 | ||||
| Station-keeping in L1/L2 | 30 – 100 | ||||
| Station-keeping in Moon orbit | 0 [1] – 400 | ||||
| Attitude control (3-axis) | 2 – 6 | ||||
| Spin-up or despin | 5 – 10 | ||||
| Stage booster separation | 5 – 10 | ||||
| Momentum wheel unloading | 2 – 6 | ||||
Earth-Moon space budget
Delta-v needed to move inside Earth Moon system (speeds lower than escape velocity) in km/s
The return to LEO figures assume that a heat shield and aerobraking/aerocapture is used to reduce the speed by up to 3. In Astrodynamics orbital station-keeping is a term used to describe a particular set of Orbital maneuvers used to keep a spacecraft in assigned Orbit A geostationary orbit (GEO is a Geosynchronous orbit directly above the Earth 's Equator (0° Latitude) with a period equal to the Earth's In Physics, escape velocity is the speed where the Kinetic energy of an object is equal to the magnitude of its Gravitational potential energy A heat shield is a protective layer on a Spacecraft or Ballistic missile that is designed to protect it from the high Temperature of Atmospheric Aerobraking is a Spaceflight maneuver that reduces the high point of an Elliptical orbit ( Apoapsis) by flying the vehicle through the Atmosphere Aerocapture is a technique used to reduce Velocity of a spacecraft arriving at a Celestial body with a Hyperbolic trajectory, in order to bring it 2 km/s. The heat shield increases the mass, possibly by 15%. Where a heat shield is not used the higher from LEO Delta-v figure applies.
| From\To | LEO-Ken | LEO-Eq | GEO | EML-1 | EML-2 | EML-4/5 | LLO | Moon | C3 |
|---|---|---|---|---|---|---|---|---|---|
| Earth | 9. EARTH was a short-lived Japanese vocal trio which released 6 singles and 1 album between 2000 and 2001 3 - 10 | ||||||||
| Low Earth Orbit (LEO-Ken) | 4. A Low Earth Orbit (LEO is generally defined as an Orbit within the locus extending from the Earth’s surface up to an altitude of 2000 km 24 | 4. 33 | 3. 77 | 3. 43 | 3. 97 | 4. 04 | 5. 93 | 3. 22 | |
| Low Earth Orbit (LEO-Eq) | 4. A Low Earth Orbit (LEO is generally defined as an Orbit within the locus extending from the Earth’s surface up to an altitude of 2000 km 24 | 3. 90 | 3. 77 | 3. 43 | 3. 99 | 4. 04 | 5. 93 | 3. 22 | |
| Geostationary Orbit (GEO) | 2. A geostationary orbit (GEO is a Geosynchronous orbit directly above the Earth 's Equator (0° Latitude) with a period equal to the Earth's 06 | 1. 63 | 1. 38 | 1. 47 | 1. 71 | 2. 05 | 3. 92 | 1. 30 | |
| Lagrangian point 1 (EML-1) | 0. 77 | 0. 77 | 1. 38 | 0. 14 | 0. 33 | 0. 64 | 2. 52 | 0. 14 | |
| Lagrangian point 2 (EML-2) | 0. 33 | 0. 33 | 1. 47 | 0. 14 | 0. 34 | 0. 64 | 2. 52 | 0. 14 | |
| Lagrangian point 4/5 (EML-4/5) | 0. 84 | 0. 98 | 1. 71 | 0. 33 | 0. 34 | 0. 98 | 2. 58 | 0. 43 | |
| Low Lunar orbit (LLO) | 1. In Astronomy, lunar orbit (also known as a Selenocentric orbit) refers to the orbit of an object around the Moon. 31 | 1. 31 | 2. 05 | 0. 64 | 0. 65 | 0. 98 | 1. 87 | 1. 40 | |
| Moon (Moon) | 2. 74 | 2. 74 | 3. 92 | 2. 52 | 2. 53 | 2. 58 | 1. 87 | 2. 80 | |
| Earth Escape velocity (C3) | 0. EARTH was a short-lived Japanese vocal trio which released 6 singles and 1 album between 2000 and 2001 In Physics, escape velocity is the speed where the Kinetic energy of an object is equal to the magnitude of its Gravitational potential energy 00 | 0. 00 | 1. 30 | 0. 14 | 0. 14 | 0. 43 | 1. 40 | 2. 80 | |
Interplanetary budget
| From | To | delta-v in km/s |
|---|---|---|
| Earth Escape velocity (C3) | Mars Transfer Orbit | 0. EARTH was a short-lived Japanese vocal trio which released 6 singles and 1 album between 2000 and 2001 In Physics, escape velocity is the speed where the Kinetic energy of an object is equal to the magnitude of its Gravitational potential energy In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions 6 |
| Mars Transfer Orbit | Mars Capture Orbit | 0. In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions A capture orbit is a reverse Escape orbit. It is a Parabolic orbit with as special case a straight line in the direction of the center of the central body 9 |
| Mars Capture Orbit | Deimos Transfer Orbit | 0. A capture orbit is a reverse Escape orbit. It is a Parabolic orbit with as special case a straight line in the direction of the center of the central body TemplateInfobox Planet.--> Deimos (ˈdaɪməs; also /ˈdiːməs/ In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions 2 |
| Deimos Transfer Orbit | Deimos surface | 0. TemplateInfobox Planet.--> Deimos (ˈdaɪməs; also /ˈdiːməs/ In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions TemplateInfobox Planet.--> Deimos (ˈdaɪməs; also /ˈdiːməs/ 7 |
| Deimos Transfer Orbit | Phobos Transfer Orbit | 0. TemplateInfobox Planet.--> Deimos (ˈdaɪməs; also /ˈdiːməs/ In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions 3 |
| Phobos Transfer Orbit | Phobos surface | 0. In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions 5 |
| Mars Capture Orbit | Low Mars Orbit | 1. A capture orbit is a reverse Escape orbit. It is a Parabolic orbit with as special case a straight line in the direction of the center of the central body In Physics, an orbit is the gravitationally curved path of one object around a point or another body for example the gravitational orbit of a planet around a star 4 |
| Low Mars Orbit | Mars surface | 4. In Physics, an orbit is the gravitationally curved path of one object around a point or another body for example the gravitational orbit of a planet around a star 1 |
| Earth Escape velocity (C3) | Closest NEO Asteroids[5] | 0. EARTH was a short-lived Japanese vocal trio which released 6 singles and 1 album between 2000 and 2001 In Physics, escape velocity is the speed where the Kinetic energy of an object is equal to the magnitude of its Gravitational potential energy Near-Earth objects ( NEOs) are Asteroids Comets and large Meteoroids whose orbits bring them close ( Perihelion distance AU Asteroids, sometimes called Minor planets or planetoids', are bodies—primarily of the inner Solar System —that are smaller than planets but 8 - 2. 0 |
According to Marsden and Ross, "The energy levels of the Sun-Earth L1 and L2 points differ from those of the Earth-Moon system by only 50 m/s (as measured by maneuver velocity). "[6]
Delta-vs between Earth and Mars
Abbreviations used
| C3 | Escape orbit |
| GEO | Geosynchronous orbit |
| GTO | Geostationary transfer orbit |
| L5 | Earth-Moon fifth Lagrangian point |
| LEO-Eq | Low Earth orbit - equatorial |
| LEO-Ken | Low Earth orbit - "Kennedy inclination orbit" |
See also
References
- ^ Frozen lunar orbits
- ^ list of delta-v
- ^ L2 Halo lunar orbit
- ^ Strategic Considerations for Cislunar Space Infrastructure
- ^ NEO list
- ^ New methods in celestial mechanics and mission design. An escape orbit (also known as C 3 = 0 orbit is a high-energy Parabolic orbit around the central body A geosynchronous orbit is an Orbit around the Earth with an Orbital period matching the Earth's sidereal rotation period A Geosynchronous Transfer Orbit or Geostationary Transfer Orbit ( GTO) is a Hohmann transfer orbit around the Earth between a Low Earth orbit A Low Earth Orbit (LEO is generally defined as an Orbit within the locus extending from the Earth’s surface up to an altitude of 2000 km A Low Earth Orbit (LEO is generally defined as an Orbit within the locus extending from the Earth’s surface up to an altitude of 2000 km The John F Kennedy Space Center ( KSC) is the NASA Space vehicle launch facility and Launch Control Center ( Spaceport) on In Astronautics and Aerospace engineering, the bi-elliptic transfer is an Orbital maneuver that moves a Spacecraft from one Orbit In Orbital mechanics and Aerospace engineering, a gravitational slingshot, gravity assist or swing-by is the use of the relative movement and In Astronautics and Aerospace engineering, the Hohmann transfer orbit is an Orbital maneuver using two engine impulses which under standard assumptions The Oberth effect is a feature of Astronautics where using a Rocket engine close to a gravitational body gives a higher final speed than the same burn executed further Tsiolkovsky's rocket equation, or ideal rocket equation is named after Konstantin Tsiolkovsky, who independently derived it and published in his 1903 work considers Bull. Amer. Math. Soc. .
- ^ table of cislunar/mars delta-vs
- ^ cislunar delta-vs
External links
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